跨声速多级轴流压气机非设计性能预测  

Off-design performance prediction of multi-stage transonic axial compressor

作　　者：杜文海[1] 吴虎[1] 黄健[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2007年第9期1481-1486,共6页Journal of Aerospace Power

摘　　要：基于公开发表的研究成果,发展了一种适用于跨声速轴流压气机的新型损失和落后角模型,并进行了3-D的修正,运用改进的流线曲率法对某两级跨声速轴流压气机进行了数值模拟,得到了设计点和非设计点的特性曲线.通过计算结果与实验值的比较,验证了本模型和方法在设计点和非设计点均具较高的精度,可用于工程计算.A new loss and deviation model suitable for multi-stage transonic axial compressor was developed according to the research findings publicly available. Along with 3-D modification, numerical simulation was performed for two-stage transonic axial compressor using an improved streamline curvature method, thus obtaining the characteristic curve of design point and off-design point. By combining the calculated results with experimental value, this model and method are suitable for engineering calculation with higher accuracy of design point and off-design point.

关 键 词：航空、航天推进系统 流线曲率法 跨声速 轴流压气机 非设计 损失落后角模型 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]